摘要
针对固体火箭发动机难以实现推力调节和能量控制,限制导弹射程和滞空时间的问题,采用隔舱式脉冲发动机设计,提出了一种可行的三脉冲的发动机结构方案,详细介绍了发动机总体方案及工作过程,完成了硬质隔板选材与结构设计,通过原理样机对隔板方案进行了单项试验考核,最终成功实现了发动机的三级脉冲工作。
Solid rocket motor thrust regulation and energy control is difficult to achieve, and the missile range and endurance was greatly limited. Multiple pulse solid rocket motor with port cover can effectively realize the engine energy management. In this paper, a feasible structure scheme of three pulse engine was presented, and the overall scheme and the working process was introduced. Then, the port cover＇ s material selection and structure design was completed. Finally, the port cover scheme was examined with a single test using the principle engine, and the three pulse engine operation was successfully implemen-ted.
出处
《战术导弹技术》
北大核心
2015年第4期59-65,共7页
Tactical Missile Technology
关键词
固体火箭发动机
多脉冲
陶瓷隔板
solid rocket motor
multiple pulse
ceramic port cover
